US3903959A - Gas turbine engine heat regenerator - Google Patents

Gas turbine engine heat regenerator Download PDF

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US3903959A
US3903959A US388173A US38817373A US3903959A US 3903959 A US3903959 A US 3903959A US 388173 A US388173 A US 388173A US 38817373 A US38817373 A US 38817373A US 3903959 A US3903959 A US 3903959A
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Prior art keywords
porous layer
seal member
impregnated
gas turbine
turbine engine
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US388173A
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Shingi Fushimi
Katsuhiro Kishida
Hiroyuki Aoki
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Nissan Motor Co Ltd
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Nissan Motor Co Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F02C7/10—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers
    • F02C7/105—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers of the rotary type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D19/00—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium
    • F28D19/04—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium using rigid bodies, e.g. mounted on a movable carrier
    • F28D19/047—Sealing means
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S165/00—Heat exchange
    • Y10S165/009—Heat exchange having a solid heat storage mass for absorbing heat from one fluid and releasing it to another, i.e. regenerator
    • Y10S165/013—Movable heat storage mass with enclosure
    • Y10S165/016—Rotary storage mass
    • Y10S165/02—Seal and seal-engaging surface are relatively movable
    • Y10S165/025—Heat resistant material seal

Definitions

  • ABSTRACT A fixed seal member and a rotary matrix member
  • This invention relates to an improved gas turbine engine heat regenerator and, more particularly, to a disc type rotary heat regenerator for a gas turbine engine having a seal member and a matrix member whose contacting sliding surfaces have porous layers impregnated with a heat-resisting lubricant, and a method of forming the porous layers.
  • a disc type heat regenerator for a gas turbine engine commonly has a seal member fixed in the housing of the gas turbine engine and a matrix member made of a ceramic material rotatably mounted in the housing of the gas turbine.
  • the matrix member is so disposed that it slidably contacts the seal member and rotates in close contact therewith under high pressure.
  • a working medium such as air passes from a compressor to a combustor through the seal and matrix members, and is heated by hot engine exhaust gas also passing therethrough, as is well known by those skilled in the art.
  • the seal member prevents leakage of the working medium.
  • the seal member and the matrix member are subjected to high temperature and friction which may cause extreme wear. Therefore, they must resist this friction and wear at high temperature and, in addition, must withstand considerably rapid temperature changes during normal operation as well as a rapid temperature rise when the engine starts.
  • a sintered material made from, for example, a mixture of a metal oxide and a fluoride, phosphate, or borate of an alkaline-earth group lla metal, or a refractory metal material sprayed with the aforementioned mixture has been used.
  • this prior art has the disadvantages that the seal member itself wears greatly due to friction with the matrix member at high temperature (approx. 500C to 700C), and the ce amic matrix member also wears at a substantial rate with the consequent result that it becomes difficult to maintain sufficient sealing ability for a long duration.
  • a disc type rotary heat regenerator for a gas turbine engine having a housing, which comprises a seal member fixed in the housing and a matrix member rotatably mounted in sliding contact with the seal member, the contacting surfaces of the two members having layers of porous material. f the two porous layers, at least the porous layer of the seal member is impregnated with a heat resisting lubricant.
  • a method of forming an impregnated porous layer on the surface of the seal member which comprises the step of applying an undercoating material onto the surface of the seal member, the step of spraying powder particles of a mixture comprising a first material selected from the group consisting of nickel oxide and cobalt oxide and a second material selected from the group consisting of alkaline-earth metal fluoride, phosphate and borate onto the surface of the seal member, and the step of impregnating the porous layer with a heat resisting lubricant selected from the group consisting of graphite, molybdenum disulphide, tungsten disulphide, boron nitride and sericite.
  • FIG. 1 is an exploded perspective view of one embodiment of a seal member and matrix member assembly of a conventional disc type rotary heat regenerator to an improvement of which the present invention is directed;
  • FIG. 2 is a diagram showing the relationship between the porosity of the porous layer of the seal member and the spraying distance
  • FIGS. 3 to 5 are diagrams showing the relationship between the depth of wear of porous layers of seal members according to this invention as a function of elapsed time under various conditions;
  • FIG. 6 is an optical microstructure (X) view of a section of a sprayed porous layer on an undercoated seal member according to the present invention.
  • FIG. 7 is an optical microstructure (X100) view of the sliding surface of a matrix member according to the present invention.
  • a seal member generally indicated as l is fixed in a housing (not shown) of a gas turbine engine (not shown). It is preferably divided into two parts la and 1b. The parts la and lb have openings 1c and la, respectively.
  • an impregnated porous layer 1e is formed on the rear surfaces (as shown) of the parts la and lb of the seal member I. The surface of the impregnated porous layer acts as a sliding surface.
  • a matrix member generally indicated as 2 is rotatably mounted in the housing of the gas turbine engine.
  • the matrix member 2 has a honeycomb structure 20 consisting of flat plates and corrugated plates (no numerals), and a hub 2b situated in the center of the honeycomb structure 2a for receiving a driving shaft (not shown).
  • a casing 20 surrounds the honeycomb structure 2a. End surfaces of the honeycomb structure 1a, hub 2b and easing 2c act as sliding surfaces which slidably engage with the surface of the porous layer 1e of the seal member 1.
  • the matrix member 2 is rotated relative to the seal member 1 with respective sliding surfaces in close contact with each other.
  • a working medium such as air flows from a compressor (not shown) to a combustor (not shown) through the opening 1c of the seal member 1 and the matrix member 2. While flowing through the matrix member 2, the working medium is preheated by hot turbine exhaust gas passing through the opening 1d of the seal member 1 and the matrix member 2. Consequently, the sliding surfaces of the seal member 1 and matrix member 2 are subjected to high friction and high temperature.
  • the porous layer of the seal member 1 is formed and impregnated as follows: An undercoating material such as powdered nickel aluminite is first sprayed onto the designated surface of the seal member. Then, a mixture of powders of nickel oxide and calcium fluoride is sprayed onto the undercoated surface of the seal member.
  • the grain size of the powders is suitably selected.
  • the content of nickel oxide is preferably 75 to 90% by weight and that of calcium fluoride is preferably to 25% by weight. If the content of nickel oxide is higher than 90% and that of calcium fluoride is lower than 10%, the spraying efficiency will deteriorate at high temperature.
  • the porosity of the sprayed porous layer is preferably 20 to 30% by volume, and can be adjusted by varying the spraying distance. If the porosity is higher than 30%, the sprayed porous layer will become brittle. A porosity of less than 20% is difficult to obtain.
  • Nickel oxide may be replaced by cobalt oxide, and calcium fluoride may be replaced by, an alkaline-earth metal fluoride, phosphate or borate.
  • the porous layer is impregnated with a heat resisting lubricant such as graphite, molybdenum disulphide, tungsten disulphide, boron nitride or sericite.
  • a heat resisting lubricant such as graphite, molybdenum disulphide, tungsten disulphide, boron nitride or sericite.
  • a matrix member is usually made of a ceramic and, therefore, is itself porous. Accordingly, in this case, it is not necessary to form a sprayed porous layer on the matrix member. It will suflice to impregnate the ceramic matrix member with a heat resisting lubricant.
  • FIG. 2 is a diagram showing the relationship between the spraying distance and the porosity of a sprayed porous layer.
  • FIG. 6 shows the optical microstructure of a section of a sprayed porous layer which was formed by spraying the particles from a distance of 150 mm.
  • the obtained porosity was In the photograph, porous regions appear as black.
  • the seal mem' ber with a sprayed porous layer thus formed was immersed in a solution of boron nitride in alcohol under vacuum thereby impregnating the porous layer with boron nitride.
  • the seal member thus impregnated was fully dried, and was then rotated relative to and in abutting sliding contact with a ceramic matrix member at a temperature of 500C, surface pressure of 350 to 360g/cm and a peripheral speed of m/m for a predetermined time. Then the amount of wear of the seal member was measured.
  • FIG. 3 shows the relationship between the depth of wear (u) and elapsed time.
  • a curve 1 represents the wear of a seal member having a nonimpregnated porous layer with a porosity of 25%
  • a curve 2 shows the wear of a seal member having a porous layer with a porosity of 53% impregnated with boronnitride.
  • a curve 3 shows the wear of a seal member having a porous layer with a porosity of 35% impregnated with boron-nitride
  • a curve 4 shows the wear of a seal member having a porous layer with a porosity of 42% impregnated with boron-nitride
  • a curve 5 shows the wear of a seal member having a porous layer with a porosity of 25% impregnated with boron-nitride.
  • the porosities 25%, 53%, 35%, and 42% mentioned above correspond to spraying distances of 150 mm, 200 mm, mm and 50mm, respectively.
  • EXAMPLE 2 After a powdered mixture of nickel oxide and calcium fluoride was sprayed onto a seal member using the same method as that of Example I, to form a porous layer having a porosity of about 25%, the porous layer was impregnated with molybdenum disulphide, tungsten disulphide, sericite or graphite. The seal member thus impregnated was rotated in sliding abutting contact with the ceramic matrix member under the same conditions as in Example 1.
  • FIG. 4 shows the relationship between the wear depth and elapsed time of the seal member. The sprayed porous layer had a porosity of 24 to 28%. In the diagram of FIG.
  • a curve 1 illustrates the wear of a seal member having a porous layer not impregnated
  • a curve 2 shows the wear of a seal member having a porous layer impregnated with sericite
  • a curve 3 shows the wear of a seal member having a porous layer impregnated with tungsten disulphide
  • a curve 4 shows the wear of a seal member having a porous layer impregnated with molybdenum Clisulphide
  • a curve 5 shows the wear of a seal member having a porous layer impregnated with graphite.
  • FIG. 7 shows the optical microstructure of a section of a ceramic matrix member.
  • the matrix member was impregnated with boron nitride by the same method as that of Example 1.
  • a seal member with a porous layer was rotated in abutting sliding contact with the impregnated ceramic matrix member for a predetermined time. Then the amount of wear of the seal member was measured.
  • FIG. 5 shows the relationship between the wear and elapsed time of the seal member.
  • the spraying material was a mixture of 80% by weight nickel oxide and by weight calcium fluoride, the spraying distance was 150 mm, and the test conditions were 500C, 350 to 3vt30g/cm surface pressure and peripheral speed 30 m/m, which were the same as those in Example 1.
  • the results are shown in FIG. 5 in the same way as in FIG. 3.
  • a curve 1 shows the wear of a seal member having a non-impregnated sprayed porous layer
  • a curve 2 the wear of a seal member having a porous layer impregnated with boron nitride.
  • the wear ofa seal member having its sprayed porous layer impregnated is almost one-fifth that of a seal member having a sprayed porous layer not impregnated.
  • the ceramic matrix member in this example has not worn at all and can maintain sufficient sealing capacity for a long time. Since only the porous portion of the sliding surface of the matrix member is impregnated with boron nitride, the area of the flow passageways of the matrix member is not reduced, nor are the heat exchanging capacity and durability thereof decreased.
  • a matrix member and seal member for a gas turbine engine of the present invention have the advantage that the amount of wear of the seal member can be reduced to about one-half to one-fifth that of a conventional design at high temperature, and in addition the matrix member is not worn at all thereby providing extremely stable sealing performance and superior lubricating ability for a long time.
  • a disc type rotary heat regenerator for a gas turbine engine having a housing and comprising a seal member fixed in said housing, a first porous layer formed on a surface of said member and having a porosity of 20% to 30% by volume, said first porous layer being formed of a mixture of powders, comprising a first material selected from the group consisting of nickel oxide and cobalt oxide, and a second material selected from the group consisting of alkaline-earth metal fluoride, phosphate and borate, a matrix member rotatably mounted in said housing, a second porous layer formed on a surface of said matrix member, said matrix member being rotatable relative to said seal member with said first and second porous layers in abutting contact with each other, and a heat resisting lubricant, at least said first porous layer being impregnated with said heat resisting lubricant, said heat resisting lubricant being selected from the group consisting of graphite, molybdenum disulphide, tungsten disulphide
  • a disc type rotary heat regenerator for a gas tur bine engine as claimed in claim 1 said matrix member being made of a ceramic.
  • a disc type rotary heat regenerator for a gas turbine engine as claimed in claim 4 said ceramic matrix member being impregnated with said heat resisting lubricant consisting of graphite, molybdenum disulphide,

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Gasket Seals (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

A fixed seal member and a rotary matrix member whose contacting sliding surfaces have porous layers impregnated with a heatresisting lubricant, and a method of forming the porous layers.

Description

Sept. 9, 1975 United States Patent [191 Fushimi et al.
[ GAS TURBINE ENGINE HEAT REGENERATOR Silvcrslone ct al.
WM a c mm 223 7777 9999 HUN 4355 83 8 0963 29 6690 7M53 3333 [75] Inventors: Shingi Fushimi, Yokosuka;
Katsuhiro Kishida; l-liroyuki Aoki, both of Yokohama, all of Japan 99 MW mm 8. M mm M mmm my P00 mm mum mm m. EUU T mm 99 Nun 039 m 79 ma 40 37 66 a m a .h 0 k 0 Y m L o C 3 m 7 9 m 1 M 4 www NJA e .m m a m A m.- H .4 7 2 [21] Appi. No.: 388,173
Primary ExaminerAlbert W. Davis, Jr.
[57] ABSTRACT A fixed seal member and a rotary matrix member [30] Foreign Appllcalion Priority Data Aug 15, I972 ma Wd an 3 s i mn m m mm b e m J dam u o S r mmy .m d h t s g m mm uwm c m mwf n f d 0. 0 mm h e wim 707 2 2 m 1 6 7 2MB 7 6 w 7 MN 2 5 ;m6 N 5 H 6 m l H Wmh c r mm 0 & .M UmF 5 Claims, 7 Drawing Figures PATENTEI] SEP T 91975 SHEET 1 [IF 3 g 50 T 40 g 30 H9. 2 8 cc 20 8 IO 50 I00 :50 200 SPRAYING DISTANCE (mm) Fig. 3 90+ I 80 SPRAYING MATERlAL NiO C0F2=8O 2O A T TEMPERATUREI 500C 1 7O SLRFACE PRESSURE: 350-3609/cm PERIPHERAL SPEED: 30 /min K 00 2 g 50 40- E5 30- I E 20 63 10 0 v T T T IO 205040 5060708090|OO TIME (Hrs) PATENTEBSEP 9:975
sum 2 [1F 3 Fig. 4
SPRAYTNG MATERIAL NiO CuFg 80 POROS ITY f 24 28 /o TEMPERATURE 3 500 C 2 SURFACE PRESSURE I 350 600g cm PERIPHERAL SPEED 1 /min.
[O 20 5'0 4'0. 5'0 6'0 7'0 80 9O :00 TIME (Hrs) Fig. 5
SPRAYTNG MATERTALI Macaw 80 20 SPRAYTNG DISTANCEI I50 mm TEMPERATURE 500 C SURFACE PRESSURE (3-36Og/cm PERIPHERAL SPEED 1 /mi n 1O 20 5'0 4'0 50 6O 9'0 I00 TIME (Hrs) PAIENTEDSEP arms 3. 903.959
sumaurs SFRAYING MATERIAL? NiO COFZ =8O ZO POROSITY 1 24 SPRAYING DISTANCE ISO mm NiO, CGFZ sRRAYED LAYER NICKEL ALUMINITE UN DERCOATI NG l8-8 STAINLESS STEEL Fig. 7
CORRBGATED PLATE CORRUGATED PLATE GAS TURBINE ENGINE HEAT REGENERATOR This invention relates to an improved gas turbine engine heat regenerator and, more particularly, to a disc type rotary heat regenerator for a gas turbine engine having a seal member and a matrix member whose contacting sliding surfaces have porous layers impregnated with a heat-resisting lubricant, and a method of forming the porous layers.
As is well known, a disc type heat regenerator for a gas turbine engine commonly has a seal member fixed in the housing of the gas turbine engine and a matrix member made of a ceramic material rotatably mounted in the housing of the gas turbine. The matrix member is so disposed that it slidably contacts the seal member and rotates in close contact therewith under high pressure. A working medium such as air passes from a compressor to a combustor through the seal and matrix members, and is heated by hot engine exhaust gas also passing therethrough, as is well known by those skilled in the art. During this operation, the seal member prevents leakage of the working medium. As is apparent from the foregoing, the seal member and the matrix member are subjected to high temperature and friction which may cause extreme wear. Therefore, they must resist this friction and wear at high temperature and, in addition, must withstand considerably rapid temperature changes during normal operation as well as a rapid temperature rise when the engine starts.
Heretofore, for a seal member of this type, a sintered material made from, for example, a mixture of a metal oxide and a fluoride, phosphate, or borate of an alkaline-earth group lla metal, or a refractory metal material sprayed with the aforementioned mixture has been used. However, this prior art has the disadvantages that the seal member itself wears greatly due to friction with the matrix member at high temperature (approx. 500C to 700C), and the ce amic matrix member also wears at a substantial rate with the consequent result that it becomes difficult to maintain sufficient sealing ability for a long duration.
It is, therefore, an object of the present invention to provide a heat regenerator which is highly stable in operation by eliminating the aforementioned disadvantages of the prior art.
It is another object of the present invention to provide a heat regenerator having a seal member and a matrix member which have superior lubricating properties and wear resisting characteristics at high temperature, and long operating lifetimes.
According to the present invention, there is provided a disc type rotary heat regenerator for a gas turbine engine having a housing, which comprises a seal member fixed in the housing and a matrix member rotatably mounted in sliding contact with the seal member, the contacting surfaces of the two members having layers of porous material. f the two porous layers, at least the porous layer of the seal member is impregnated with a heat resisting lubricant.
According to the present invention, there is also provided a method of forming an impregnated porous layer on the surface of the seal member which comprises the step of applying an undercoating material onto the surface of the seal member, the step of spraying powder particles of a mixture comprising a first material selected from the group consisting of nickel oxide and cobalt oxide and a second material selected from the group consisting of alkaline-earth metal fluoride, phosphate and borate onto the surface of the seal member, and the step of impregnating the porous layer with a heat resisting lubricant selected from the group consisting of graphite, molybdenum disulphide, tungsten disulphide, boron nitride and sericite.
These and other objects, features and advantages of the present invention will become more fully apparent from the following description taken in conjunction with the accompanying drawings, in which' FIG. 1 is an exploded perspective view of one embodiment of a seal member and matrix member assembly of a conventional disc type rotary heat regenerator to an improvement of which the present invention is directed;
FIG. 2 is a diagram showing the relationship between the porosity of the porous layer of the seal member and the spraying distance;
FIGS. 3 to 5 are diagrams showing the relationship between the depth of wear of porous layers of seal members according to this invention as a function of elapsed time under various conditions;
FIG. 6 is an optical microstructure (X) view of a section of a sprayed porous layer on an undercoated seal member according to the present invention; and
FIG. 7 is an optical microstructure (X100) view of the sliding surface of a matrix member according to the present invention.
Referring to FIG. 1, a seal member generally indicated as l is fixed in a housing (not shown) ofa gas turbine engine (not shown). It is preferably divided into two parts la and 1b. The parts la and lb have openings 1c and la, respectively. In addition, an impregnated porous layer 1e is formed on the rear surfaces (as shown) of the parts la and lb of the seal member I. The surface of the impregnated porous layer acts as a sliding surface. A matrix member generally indicated as 2 is rotatably mounted in the housing of the gas turbine engine. The matrix member 2 has a honeycomb structure 20 consisting of flat plates and corrugated plates (no numerals), and a hub 2b situated in the center of the honeycomb structure 2a for receiving a driving shaft (not shown). A casing 20 surrounds the honeycomb structure 2a. End surfaces of the honeycomb structure 1a, hub 2b and easing 2c act as sliding surfaces which slidably engage with the surface of the porous layer 1e of the seal member 1.
In operation, the matrix member 2 is rotated relative to the seal member 1 with respective sliding surfaces in close contact with each other. As is well known, a working medium such as air flows from a compressor (not shown) to a combustor (not shown) through the opening 1c of the seal member 1 and the matrix member 2. While flowing through the matrix member 2, the working medium is preheated by hot turbine exhaust gas passing through the opening 1d of the seal member 1 and the matrix member 2. Consequently, the sliding surfaces of the seal member 1 and matrix member 2 are subjected to high friction and high temperature.
According to this invention, the porous layer of the seal member 1 is formed and impregnated as follows: An undercoating material such as powdered nickel aluminite is first sprayed onto the designated surface of the seal member. Then, a mixture of powders of nickel oxide and calcium fluoride is sprayed onto the undercoated surface of the seal member. The grain size of the powders is suitably selected. The content of nickel oxide is preferably 75 to 90% by weight and that of calcium fluoride is preferably to 25% by weight. If the content of nickel oxide is higher than 90% and that of calcium fluoride is lower than 10%, the spraying efficiency will deteriorate at high temperature. If the content of nickel oxide is lower than 75% and that of calcium fluoride is higher than 25%, adhesion of the sprayed porous layer will deteriorate. The porosity of the sprayed porous layer is preferably 20 to 30% by volume, and can be adjusted by varying the spraying distance. If the porosity is higher than 30%, the sprayed porous layer will become brittle. A porosity of less than 20% is difficult to obtain. Nickel oxide may be replaced by cobalt oxide, and calcium fluoride may be replaced by, an alkaline-earth metal fluoride, phosphate or borate.
After a desired sprayed porous layer is formed on the seal member, the porous layer is impregnated with a heat resisting lubricant such as graphite, molybdenum disulphide, tungsten disulphide, boron nitride or sericite.
When an impregnated porous layer is to be formed on the surface of a matrix member, the same process as described above may be adopted. However, a matrix member is usually made ofa ceramic and, therefore, is itself porous. Accordingly, in this case, it is not necessary to form a sprayed porous layer on the matrix member. It will suflice to impregnate the ceramic matrix member with a heat resisting lubricant.
The following Examples are given by way of illustra tion only, and should not be construed as limiting the scope of the invention.
EXAMPLE I After powdered nickel aluminite was sprayed onto the surface of an l8-8 stainless steel seal member to form an undercoating layer, powder particles of a mixture of 80% by weight nickel oxide and 20% by weight calcium fluoride, the particle sizes of which had been suitably selected, were sprayed thereon. The spraying process was conducted at an electric current of 400 amperes, voltage of 75 volts, hydrogen flow rate of cc/sec and nitrogen flow rate of 75 cc/sec. In addition, the spraying distance of the powder particles was varied to obtain various porous layers with different porosities. FIG. 2 is a diagram showing the relationship between the spraying distance and the porosity of a sprayed porous layer. As shown, the porosity could be varied from to 60% by varying the spraying distance of the particles. FIG. 6 shows the optical microstructure of a section of a sprayed porous layer which was formed by spraying the particles from a distance of 150 mm. The obtained porosity was In the photograph, porous regions appear as black. The seal mem' ber with a sprayed porous layer thus formed was immersed in a solution of boron nitride in alcohol under vacuum thereby impregnating the porous layer with boron nitride. The seal member thus impregnated was fully dried, and was then rotated relative to and in abutting sliding contact with a ceramic matrix member at a temperature of 500C, surface pressure of 350 to 360g/cm and a peripheral speed of m/m for a predetermined time. Then the amount of wear of the seal member was measured. The results are shown in FIG. 3, which shows the relationship between the depth of wear (u) and elapsed time. In FIG. 3, a curve 1 represents the wear of a seal member having a nonimpregnated porous layer with a porosity of 25%, a curve 2 shows the wear of a seal member having a porous layer with a porosity of 53% impregnated with boronnitride. a curve 3 shows the wear of a seal member having a porous layer with a porosity of 35% impregnated with boron-nitride, a curve 4 shows the wear of a seal member having a porous layer with a porosity of 42% impregnated with boron-nitride, and a curve 5 shows the wear of a seal member having a porous layer with a porosity of 25% impregnated with boron-nitride. The porosities 25%, 53%, 35%, and 42% mentioned above correspond to spraying distances of 150 mm, 200 mm, mm and 50mm, respectively.
As seen from these curves, the amount of wear of a seal member having a porous layer with a porosity of 35% or higher impregnated with boron-nitride (curves 2 to 4) was not much different from that ofa seal member having a porous layer non-impregnated (curve 1 However, the amount of wear of a seal member having a porous layer with a porosity of 25% impregnated with boron-nitride (curve 5) was nearly half that of a seal member having a non-impregnated porous layer with a porosity of 25% (curve I). In this case, the ceramic matrix member was not worn at all.
EXAMPLE 2 After a powdered mixture of nickel oxide and calcium fluoride was sprayed onto a seal member using the same method as that of Example I, to form a porous layer having a porosity of about 25%, the porous layer was impregnated with molybdenum disulphide, tungsten disulphide, sericite or graphite. The seal member thus impregnated was rotated in sliding abutting contact with the ceramic matrix member under the same conditions as in Example 1. FIG. 4 shows the relationship between the wear depth and elapsed time of the seal member. The sprayed porous layer had a porosity of 24 to 28%. In the diagram of FIG. 4, a curve 1 illustrates the wear of a seal member having a porous layer not impregnated, a curve 2 shows the wear of a seal member having a porous layer impregnated with sericite, a curve 3 shows the wear of a seal member having a porous layer impregnated with tungsten disulphide, a curve 4 shows the wear of a seal member having a porous layer impregnated with molybdenum Clisulphide, and a curve 5 shows the wear of a seal member having a porous layer impregnated with graphite.
As is also seen from these curves in FIG. 4, the wear of a seal member having its porous layer impregnated was nearly half that of a seal member having a porous layer not impregnated.
It is generally maintained that the lubricating ability of molybdenum disulphide and tungsten disulphide is maintained up to 400C. Therefore, if these lubricants are used at a temperature of 500C, they will partly decompose. However, since sulphur produced by the decomposition also has a lubricating capacity, the wear of the seal member having a porous layer impregnated with molybdenum disulphide or tungsten disulphide (curves 3 and 4) was one half to one-third that of a seal member having a porous layer not impregnated (curve EXAMPLE 3 FIG. 7 shows the optical microstructure of a section of a ceramic matrix member. As seen from this photograph, there exist a number of pores in the flat and corrugated plates which form the matrix member. Therefore, in this example, the matrix member was impregnated with boron nitride by the same method as that of Example 1. A seal member with a porous layer was rotated in abutting sliding contact with the impregnated ceramic matrix member for a predetermined time. Then the amount of wear of the seal member was measured. FIG. 5 shows the relationship between the wear and elapsed time of the seal member. In the case of seal members of this example, the spraying material was a mixture of 80% by weight nickel oxide and by weight calcium fluoride, the spraying distance was 150 mm, and the test conditions were 500C, 350 to 3vt30g/cm surface pressure and peripheral speed 30 m/m, which were the same as those in Example 1. The results are shown in FIG. 5 in the same way as in FIG. 3. In FIG. 5, a curve 1 shows the wear ofa seal member having a non-impregnated sprayed porous layer, and a curve 2 the wear of a seal member having a porous layer impregnated with boron nitride.
As is seen from these curves in FIG. 5, the wear ofa seal member having its sprayed porous layer impregnated is almost one-fifth that of a seal member having a sprayed porous layer not impregnated. The ceramic matrix member in this example has not worn at all and can maintain sufficient sealing capacity for a long time. Since only the porous portion of the sliding surface of the matrix member is impregnated with boron nitride, the area of the flow passageways of the matrix member is not reduced, nor are the heat exchanging capacity and durability thereof decreased.
It should be understood from the foregoing description that since a matrix member and seal member for a gas turbine engine of the present invention have the advantage that the amount of wear of the seal member can be reduced to about one-half to one-fifth that of a conventional design at high temperature, and in addition the matrix member is not worn at all thereby providing extremely stable sealing performance and superior lubricating ability for a long time.
What is claimed is:
l. A disc type rotary heat regenerator for a gas turbine engine having a housing and comprising a seal member fixed in said housing, a first porous layer formed on a surface of said member and having a porosity of 20% to 30% by volume, said first porous layer being formed of a mixture of powders, comprising a first material selected from the group consisting of nickel oxide and cobalt oxide, and a second material selected from the group consisting of alkaline-earth metal fluoride, phosphate and borate, a matrix member rotatably mounted in said housing, a second porous layer formed on a surface of said matrix member, said matrix member being rotatable relative to said seal member with said first and second porous layers in abutting contact with each other, and a heat resisting lubricant, at least said first porous layer being impregnated with said heat resisting lubricant, said heat resisting lubricant being selected from the group consisting of graphite, molybdenum disulphide, tungsten disulphide, boron nitride and sericite.
2. A disc type rotary heat regencrator for a gas turbine engine as claimed in claim 1, wherein the content of said first material in said mixture is to by weight and that of said second material is 10 to 25% by weight.
3. A disc type rotary heat regenerator for a gas turbine engine as claimed in claim 1, wherein said porous layer of said matrix member is impregnated with said heat resisting lubricant.
4. A disc type rotary heat regenerator for a gas tur bine engine as claimed in claim 1, said matrix member being made of a ceramic.
5. A disc type rotary heat regenerator for a gas turbine engine as claimed in claim 4, said ceramic matrix member being impregnated with said heat resisting lubricant consisting of graphite, molybdenum disulphide,
tungsten disulphide, boron nitride, and sericite.

Claims (5)

1. A DISC TYPE ROTARY HEAT REGENERATOR FOR A GAS TURBINE ENGINE HAVING A HOUSING AND COMPRISING A SEAL MEMBER FIXED IN SAID HOUSING, A FIRST POROUS LAYER FORMED ON A SURFACE OF SAID MEMBER AND HAVING A POROSITY OF 20% TO 30% BY VOLUME, SAID FIRST POROUS LAYER BEING FORMED OF A MIXTURE OF POWDERS, COMPRISING A FIRST MATERIAL SELECTED FROM THE GROUP CONSISTING OF NICKEL OXIDE AND COBALT OXIDE, AND A SECOND MATERIAL SELECTED FROM THE GROUP CONSISTING OF ALKALINE-EARTH METAL FLUORIDE, PHOSPHATE AND BORATE, A MATRIX MEMBER ROTATABLY MOUNTED IN SAID HOUSING, A SECOND POROUS LAYER FORMED ON A SURFACE OF SAID MTRIX MEMBER, SAID MATRIX MEMBER BEING ROTATABLE RELATIVE TO SAID MEMBER WITH SAID FIRST AND SECOND POROUS LAYERS IN ABUTTING CONTACT WITH EACH OTHER, AND A HEAT RESISTING LUBRICANT, AT LEAST SAID FIRST POROUS LAER BEING IMPREGNATED WITH SAID HEAT RESISTING LUBRICANT, SAID HEAT RESISTING LUBRICANT
2. A disc type rotary heat regenerator for a gas turbine engine as claimed in claim 1, wherein the content of said first material in said mixture is 75 to 90% by weight and that of said second material is 10 to 25% by weight.
3. A disc type rotary heat regenerator for a gas turbine engine as claimed in claim 1, wherein said porous layer of said matrix member is impregnated with said heat resisting lubricant.
4. A disc type rotary heat regenerator for a gas turbine engine as claimed in claim 1, said matrix member being made of a ceramic.
5. A disc type rotary heat regenerator for a gas turbine engine as claimed in claim 4, said ceramic matrix member being impregnated with said heat resisting lubricant consisting of graphite, molybdenum disulphide, tungsten disulphide, boron nitride, and sericite.
US388173A 1972-08-15 1973-08-14 Gas turbine engine heat regenerator Expired - Lifetime US3903959A (en)

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4093243A (en) * 1975-08-29 1978-06-06 Nissan Motor Company Limited Rubbing contact seal member with low wear coating and metal-containing undercoat
US4226429A (en) * 1977-12-15 1980-10-07 Nissan Motor Company, Limited Fluid seal for use in rotary regenerator
US4391450A (en) * 1982-08-30 1983-07-05 Electrochemical Technology Corp. Shaft seal resistant to electrokinetic corrosion
US4762330A (en) * 1985-04-10 1988-08-09 Goetze Ag Sealing ring
US4997192A (en) * 1987-12-28 1991-03-05 Tanken Seiko Kabushiki Kaisha Mechanical seal using pore-dispersed material, and pore-dispersed cemented carbide and method for manufacturing same
US5145011A (en) * 1989-07-19 1992-09-08 NGK Insulations, Ltd. Sealing members for use in gas preheater
US5234048A (en) * 1991-01-14 1993-08-10 Ngk Insulators, Ltd. Sealing members for gas preheaters, and sealing structures using such sealing members for gas preheaters
US5421594A (en) * 1991-02-14 1995-06-06 Marine & Petroleum Mfg., Inc. Gasket
US6092811A (en) * 1996-04-30 2000-07-25 Jamco Products, Llc Hybrid gasket
US20040096689A1 (en) * 2001-05-07 2004-05-20 Althoefer Kait Sheet-metal foil with sliding structure, honeycomb body and process for producing the same
US20190353249A1 (en) * 2018-05-15 2019-11-21 Dell Products L.P. Airflow sealing by flexible rubber with i-beam and honeycomb structure

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5814407B2 (en) * 1976-05-10 1983-03-18 ライオン株式会社 Method for producing catalyst for olefin polymerization
JPS5877827A (en) * 1981-10-31 1983-05-11 Toshinobu Higashimura Oligomerization of alpha-olefin
JPS58187794A (en) * 1982-04-28 1983-11-02 Nissan Motor Co Ltd Rotary heat storage type heat exchanger
JP3000125B2 (en) * 1994-05-17 2000-01-17 科学技術庁航空宇宙技術研究所長 Rotary heat exchanger

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3576208A (en) * 1969-09-02 1971-04-27 Ford Motor Co Gas turbine heat exchanger and method of making
US3646993A (en) * 1970-05-18 1972-03-07 Gen Motors Corp Stabilized nickel oxide seal
US3659861A (en) * 1970-07-06 1972-05-02 Ford Motor Co Particulate coating for the rubbing seal of a gas turbine regenerator
US3730538A (en) * 1970-06-26 1973-05-01 Leyland Gas Turbines Ltd Rubbing seal for a rotary regenerative heat exchanger

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3497376A (en) * 1966-10-10 1970-02-24 Us Air Force Method for application of solid lubricant coatings

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3576208A (en) * 1969-09-02 1971-04-27 Ford Motor Co Gas turbine heat exchanger and method of making
US3646993A (en) * 1970-05-18 1972-03-07 Gen Motors Corp Stabilized nickel oxide seal
US3730538A (en) * 1970-06-26 1973-05-01 Leyland Gas Turbines Ltd Rubbing seal for a rotary regenerative heat exchanger
US3659861A (en) * 1970-07-06 1972-05-02 Ford Motor Co Particulate coating for the rubbing seal of a gas turbine regenerator

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4093243A (en) * 1975-08-29 1978-06-06 Nissan Motor Company Limited Rubbing contact seal member with low wear coating and metal-containing undercoat
US4226429A (en) * 1977-12-15 1980-10-07 Nissan Motor Company, Limited Fluid seal for use in rotary regenerator
US4391450A (en) * 1982-08-30 1983-07-05 Electrochemical Technology Corp. Shaft seal resistant to electrokinetic corrosion
US4762330A (en) * 1985-04-10 1988-08-09 Goetze Ag Sealing ring
US4997192A (en) * 1987-12-28 1991-03-05 Tanken Seiko Kabushiki Kaisha Mechanical seal using pore-dispersed material, and pore-dispersed cemented carbide and method for manufacturing same
US5316072A (en) * 1989-07-19 1994-05-31 Ngk Insulators, Ltd. Sealing members for use in gas preheater
US5145011A (en) * 1989-07-19 1992-09-08 NGK Insulations, Ltd. Sealing members for use in gas preheater
US5234048A (en) * 1991-01-14 1993-08-10 Ngk Insulators, Ltd. Sealing members for gas preheaters, and sealing structures using such sealing members for gas preheaters
US5421594A (en) * 1991-02-14 1995-06-06 Marine & Petroleum Mfg., Inc. Gasket
US6092811A (en) * 1996-04-30 2000-07-25 Jamco Products, Llc Hybrid gasket
US20040096689A1 (en) * 2001-05-07 2004-05-20 Althoefer Kait Sheet-metal foil with sliding structure, honeycomb body and process for producing the same
US7101602B2 (en) * 2001-05-07 2006-09-05 Emitec Gesellschaft Fuer Emissionstechnologie Mbh Sheet-metal foil with sliding structure, honeycomb body and process for producing the same
US20190353249A1 (en) * 2018-05-15 2019-11-21 Dell Products L.P. Airflow sealing by flexible rubber with i-beam and honeycomb structure
US11149853B2 (en) * 2018-05-15 2021-10-19 Dell Products L.P. Airflow sealing by flexible rubber with I-beam and honeycomb structure

Also Published As

Publication number Publication date
FR2196434B1 (en) 1976-09-17
IT990247B (en) 1975-06-20
GB1432184A (en) 1976-04-14
DE2341124A1 (en) 1974-03-28
JPS4938247A (en) 1974-04-09
FR2196434A1 (en) 1974-03-15

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